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MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: MH 114 13.02% (mh114-il)
Reynolds number: 1,000,000
Max Cl/Cd: 160.95 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh114-il-1000000.txt
Download as CSV file: xf-mh114-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 114  13.02%                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0190   0.11055   0.10874  -0.1033   0.9678   0.0103
 -11.000  -0.0075   0.10677   0.10496  -0.1061   0.9642   0.0106
 -10.750   0.0026   0.10232   0.10050  -0.1099   0.9596   0.0109
 -10.500   0.0149   0.09814   0.09632  -0.1138   0.9540   0.0109
 -10.250   0.0326   0.09392   0.09208  -0.1186   0.9505   0.0110
 -10.000   0.0515   0.08972   0.08785  -0.1237   0.9456   0.0110
  -9.750   0.0706   0.08471   0.08282  -0.1297   0.9405   0.0111
  -9.500   0.0985   0.08149   0.07957  -0.1356   0.9368   0.0114
  -9.250   0.1246   0.07760   0.07564  -0.1422   0.9290   0.0114
  -8.750   0.1703   0.07094   0.06884  -0.1528   0.9071   0.0121
  -8.500   0.1817   0.06788   0.06570  -0.1555   0.8929   0.0124
  -8.250   0.1883   0.06500   0.06277  -0.1571   0.8795   0.0127
  -8.000   0.1913   0.06191   0.05963  -0.1583   0.8670   0.0130
  -7.750   0.1843   0.05662   0.05430  -0.1605   0.8538   0.0137
  -7.500   0.1770   0.05238   0.05002  -0.1614   0.8418   0.0138
  -7.250   0.0810   0.02086   0.01744  -0.1878   0.8189   0.0081
  -7.000   0.0989   0.01683   0.01281  -0.1897   0.8123   0.0077
  -6.750   0.1229   0.01451   0.01007  -0.1905   0.8069   0.0074
  -6.500   0.1491   0.01318   0.00849  -0.1909   0.8014   0.0073
  -6.250   0.1761   0.01228   0.00739  -0.1912   0.7961   0.0074
  -6.000   0.2036   0.01157   0.00653  -0.1914   0.7910   0.0074
  -5.750   0.2314   0.01096   0.00582  -0.1916   0.7857   0.0076
  -5.500   0.2594   0.01048   0.00522  -0.1918   0.7805   0.0079
  -5.250   0.2877   0.01009   0.00473  -0.1920   0.7755   0.0082
  -5.000   0.3162   0.00956   0.00411  -0.1923   0.7702   0.0089
  -4.750   0.3445   0.00927   0.00377  -0.1925   0.7649   0.0097
  -4.500   0.3729   0.00907   0.00350  -0.1927   0.7599   0.0107
  -4.250   0.4016   0.00874   0.00313  -0.1929   0.7545   0.0118
  -4.000   0.4299   0.00857   0.00291  -0.1930   0.7491   0.0136
  -3.750   0.4585   0.00836   0.00266  -0.1932   0.7438   0.0168
  -3.500   0.4872   0.00815   0.00245  -0.1934   0.7384   0.0223
  -3.250   0.5155   0.00800   0.00231  -0.1935   0.7327   0.0317
  -3.000   0.5439   0.00787   0.00219  -0.1936   0.7273   0.0443
  -2.750   0.5724   0.00771   0.00209  -0.1938   0.7215   0.0631
  -2.500   0.6006   0.00757   0.00201  -0.1940   0.7157   0.0894
  -2.250   0.6292   0.00744   0.00195  -0.1942   0.7102   0.1210
  -2.000   0.6576   0.00731   0.00190  -0.1944   0.7039   0.1578
  -1.750   0.6855   0.00723   0.00187  -0.1945   0.6979   0.1989
  -1.500   0.7141   0.00710   0.00186  -0.1948   0.6919   0.2439
  -1.250   0.7421   0.00703   0.00185  -0.1949   0.6853   0.2855
  -1.000   0.7700   0.00698   0.00186  -0.1949   0.6790   0.3268
  -0.750   0.7982   0.00691   0.00188  -0.1951   0.6722   0.3735
  -0.500   0.8255   0.00690   0.00191  -0.1950   0.6652   0.4191
  -0.250   0.8536   0.00685   0.00195  -0.1952   0.6581   0.4625
   0.000   0.8806   0.00687   0.00199  -0.1950   0.6506   0.5017
   0.250   0.9085   0.00686   0.00204  -0.1950   0.6434   0.5396
   0.500   0.9352   0.00689   0.00211  -0.1949   0.6354   0.5760
   0.750   0.9626   0.00690   0.00218  -0.1948   0.6276   0.6117
   1.000   0.9890   0.00696   0.00225  -0.1945   0.6193   0.6463
   1.250   1.0160   0.00698   0.00233  -0.1944   0.6110   0.6819
   1.500   1.0416   0.00706   0.00243  -0.1939   0.6022   0.7178
   1.750   1.0682   0.00708   0.00253  -0.1937   0.5935   0.7558
   2.000   1.0930   0.00715   0.00264  -0.1931   0.5846   0.7975
   2.250   1.1170   0.00717   0.00275  -0.1923   0.5750   0.8482
   2.500   1.1339   0.00712   0.00283  -0.1898   0.5664   0.9340
   2.750   1.1586   0.00721   0.00289  -0.1892   0.5561   1.0000
   3.000   1.1846   0.00736   0.00299  -0.1889   0.5464   1.0000
   3.250   1.2094   0.00754   0.00312  -0.1884   0.5363   1.0000
   3.500   1.2342   0.00772   0.00324  -0.1879   0.5255   1.0000
   3.750   1.2590   0.00789   0.00337  -0.1874   0.5152   1.0000
   4.000   1.2827   0.00810   0.00351  -0.1867   0.5045   1.0000
   4.250   1.3064   0.00831   0.00368  -0.1859   0.4932   1.0000
   4.500   1.3301   0.00851   0.00383  -0.1853   0.4823   1.0000
   4.750   1.3526   0.00874   0.00401  -0.1843   0.4715   1.0000
   5.000   1.3739   0.00897   0.00420  -0.1831   0.4604   1.0000
   5.250   1.3956   0.00919   0.00438  -0.1821   0.4494   1.0000
   5.500   1.4162   0.00944   0.00459  -0.1808   0.4389   1.0000
   6.000   1.4570   0.00997   0.00504  -0.1782   0.4172   1.0000
   6.250   1.4769   0.01026   0.00529  -0.1768   0.4066   1.0000
   6.750   1.5158   0.01086   0.00583  -0.1740   0.3854   1.0000
   7.000   1.5350   0.01119   0.00613  -0.1725   0.3755   1.0000
   7.500   1.5716   0.01190   0.00678  -0.1694   0.3542   1.0000
   7.750   1.5896   0.01229   0.00714  -0.1679   0.3442   1.0000
   8.250   1.6239   0.01313   0.00792  -0.1645   0.3234   1.0000
   8.500   1.6403   0.01359   0.00837  -0.1628   0.3134   1.0000
   9.000   1.6719   0.01461   0.00934  -0.1593   0.2924   1.0000
   9.250   1.6867   0.01517   0.00988  -0.1574   0.2826   1.0000
   9.750   1.7147   0.01644   0.01110  -0.1536   0.2613   1.0000
  10.000   1.7282   0.01713   0.01177  -0.1517   0.2508   1.0000
  10.250   1.7401   0.01793   0.01254  -0.1496   0.2405   1.0000
  10.500   1.7520   0.01874   0.01333  -0.1476   0.2294   1.0000
  10.750   1.7643   0.01956   0.01414  -0.1457   0.2191   1.0000
  11.000   1.7746   0.02053   0.01508  -0.1436   0.2087   1.0000
  11.250   1.7835   0.02162   0.01613  -0.1415   0.1973   1.0000
  11.500   1.7937   0.02264   0.01715  -0.1395   0.1872   1.0000
  11.750   1.8028   0.02379   0.01828  -0.1376   0.1771   1.0000
  12.000   1.8105   0.02507   0.01953  -0.1355   0.1670   1.0000
  12.250   1.8163   0.02651   0.02094  -0.1334   0.1560   1.0000
  12.500   1.8236   0.02790   0.02232  -0.1315   0.1463   1.0000
  12.750   1.8305   0.02936   0.02378  -0.1296   0.1375   1.0000
  13.000   1.8356   0.03102   0.02542  -0.1278   0.1288   1.0000
  13.250   1.8420   0.03263   0.02703  -0.1261   0.1208   1.0000
  13.500   1.8467   0.03442   0.02882  -0.1244   0.1128   1.0000
  13.750   1.8495   0.03645   0.03084  -0.1226   0.1047   1.0000
  14.000   1.8542   0.03836   0.03275  -0.1212   0.0972   1.0000
  14.250   1.8562   0.04057   0.03497  -0.1196   0.0891   1.0000
  14.500   1.8565   0.04305   0.03743  -0.1182   0.0816   1.0000
  14.750   1.8590   0.04537   0.03977  -0.1169   0.0751   1.0000
  15.000   1.8593   0.04799   0.04240  -0.1157   0.0684   1.0000
  15.250   1.8583   0.05082   0.04522  -0.1146   0.0623   1.0000
  15.500   1.8593   0.05351   0.04795  -0.1137   0.0570   1.0000
  15.750   1.8574   0.05663   0.05108  -0.1128   0.0520   1.0000
  16.000   1.8573   0.05961   0.05411  -0.1122   0.0478   1.0000
  16.250   1.8547   0.06297   0.05750  -0.1116   0.0437   1.0000
  16.500   1.8536   0.06622   0.06081  -0.1112   0.0402   1.0000
  16.750   1.8499   0.06990   0.06452  -0.1110   0.0367   1.0000
  17.000   1.8482   0.07339   0.06808  -0.1109   0.0338   1.0000
  17.250   1.8430   0.07744   0.07217  -0.1109   0.0310   1.0000
  17.500   1.8411   0.08108   0.07589  -0.1110   0.0287   1.0000
  17.750   1.8348   0.08543   0.08030  -0.1114   0.0263   1.0000
  18.000   1.8307   0.08956   0.08450  -0.1118   0.0243   1.0000
  18.250   1.8248   0.09401   0.08901  -0.1125   0.0223   1.0000
  18.500   1.8182   0.09860   0.09369  -0.1133   0.0206   1.0000
  18.750   1.8125   0.10312   0.09829  -0.1142   0.0190   1.0000
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